旋流式掺混结构对补燃室二次燃烧性能的影响  

The Effects of Swirl Mixing Structure on the Second Combustion Performance of Afterburning Chamber

作　　者：陈志明[1] 周小旭[1] 张鑫[1] 白涛涛[1] 曹军伟[1] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009

出　　处：《弹箭与制导学报》2017年第3期75-79,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中设计了两种新型旋流式固冲发动机补燃室掺混结构,对该掺混结构作用下补燃室掺混燃烧流场进行了数值研究。分析了旋流式掺混结构对补燃室中掺混燃烧的影响,并与两种基准补燃室掺混结构的计算结果进行了对比分析。结果表明:旋流式掺混结构能够强化补燃室中的掺混燃烧效果,大幅提升固冲发动机补燃室的特征速度,且补燃室总压恢复系数满足设计需求,但补燃室内的旋流流动在一定程度上会削弱冲压喷管的做功能力。In this paper two new afterburning chamber mixing structures of swift solid rocket ramjet were designed, and the numerical sim- ulation of the mixed combustion flow field of afterburuing chamber under the action of the mixed structure was carried out. The effects of swirl mixing structures on mixed combustion in the afterburning chamber were analyzed and compared the calculation results with two reference afterburning chamber mixing structures. The results showed that swirl mixing structure could strengthen the the effect of the mixed combustion in the combustion chamber, and greatly enhance the characteristic velocity of solid rocket ramjet afterburning chamber. The total pressure recovery coefficient of the combustion chamber meets the design requirements, but the swirling flow in the afterburuing chamber would weaken the function of ramjet nozzle force to a certain extent.

关 键 词：固体火箭冲压发动机 补燃室 旋流 掺混燃烧 特征速度 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]